U.S. patent application number 14/439300 was filed with the patent office on 2015-10-22 for method for manufacturing a structural element having a variable thickness for aircraft production.
The applicant listed for this patent is CONSTELLIUM FRANCE. Invention is credited to Armelle Danielou, Jean-Christophe Ehrstrom, Timothy Warner.
Application Number | 20150299837 14/439300 |
Document ID | / |
Family ID | 47624155 |
Filed Date | 2015-10-22 |
United States Patent
Application |
20150299837 |
Kind Code |
A1 |
Ehrstrom; Jean-Christophe ;
et al. |
October 22, 2015 |
METHOD FOR MANUFACTURING A STRUCTURAL ELEMENT HAVING A VARIABLE
THICKNESS FOR AIRCRAFT PRODUCTION
Abstract
The invention relates to the method for manufacturing a rolled
product of variable thickness made of heat-treatable aluminum alloy
in which hot rolling is performed to achieve a variation in
thickness of at least 10% lengthwise between the thickest part and
the thinnest part; the rolled product of variable thickness
obtained undergoes solution heat-treatment and quenching with
permanent set of at least 1% in the thickest part before natural or
artificial ageing. The products obtained according to the invention
exhibit improved mechanical strength of at least 5% in the thinnest
part and improved fracture toughness of at least 15% in the
thickest part. The products according to the invention are notably
useful in the fabrication of aircraft upper or lower wing skins the
"buy to fly" ratio and the properties are simultaneously
improved.
Inventors: |
Ehrstrom; Jean-Christophe;
(Grenoble, FR) ; Danielou; Armelle; (Les Echelles,
FR) ; Warner; Timothy; (Corenc, FR) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
CONSTELLIUM FRANCE |
Paris |
|
FR |
|
|
Family ID: |
47624155 |
Appl. No.: |
14/439300 |
Filed: |
November 7, 2013 |
PCT Filed: |
November 7, 2013 |
PCT NO: |
PCT/FR2013/000287 |
371 Date: |
April 29, 2015 |
Related U.S. Patent Documents
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Application
Number |
Filing Date |
Patent Number |
|
|
61725250 |
Nov 12, 2012 |
|
|
|
Current U.S.
Class: |
428/600 ;
148/552 |
Current CPC
Class: |
C22C 21/18 20130101;
C22F 1/002 20130101; C22C 21/16 20130101; C22C 21/12 20130101; B64C
3/00 20130101; C22F 1/04 20130101; C22C 21/00 20130101; C22F 1/057
20130101; C22C 21/14 20130101 |
International
Class: |
C22F 1/057 20060101
C22F001/057; B64C 3/00 20060101 B64C003/00; C22C 21/16 20060101
C22C021/16; C22C 21/18 20060101 C22C021/18; C22F 1/00 20060101
C22F001/00; C22C 21/14 20060101 C22C021/14 |
Foreign Application Data
Date |
Code |
Application Number |
Nov 8, 2012 |
FR |
12/03006 |
Claims
1. A method for manufacturing a rolled product of variable
thickness made of heat-treatable aluminum alloy, in which a. a slab
made of heat-treatable aluminum alloy is cast, b. optionally, said
slab is homogenized, c. said optionally homogenized slab is hot
rolled, by achieving a lengthwise thickness variation to obtain a
rolled product of variable thickness, having a thicker part and a
thinner part, the difference in thickness of which is at least 10%,
d. said rolled product of variable thickness is solution
heat-treated and quenched, e. said rolled product of variable
thickness, thus solution heat-treated and quenched, is stress
relieved by controlled stretching, with a permanent set of at least
1% in the thickest part, f. the rolled product so obtained is
naturally or artificially aged.
2. The method according to claim 1 wherein the thickness of said
rolled product is between 10 mm and 50 mm and optionally between 12
mm and 30 mm.
3. The method according to claim 1 wherein the permanent set during
controlled stretching is between 1% and 3% in the thickest part and
between 4% and 6% in the thinnest part.
4. The method according to claim 1 wherein said rolled product has
two ends and the thickness of said rolled product is identical at
both of said ends, said thickest part or said thinnest part being
located at mid-length.
5. The method for manufacturing according to claim 1 wherein said
alloy is a 2XXX alloy.
6. The method according to claim 5 wherein said alloy contains at
least 0.5% lithium by weight and the metallurgical temper obtained
after artificial ageing is T8 or T8X.
7. The rolled product of variable thickness obtained by the process
according to claim 1 having a thicker part and a thinner part, the
thickness of which differs by at least 10% and having the following
properties at mid-thickness: a tensile yield stress R.sub.p0.2 (L)
in the thinnest part at least 5% greater than that in the thickest
part and a fracture toughness K.sub.1C L-T in the thickest part at
least 15% greater than that in the thinnest part.
8. The rolled product of variable thickness according to claim 7
having a thicker part and a thinner part, the thickness of which
differs by at least 10% and the thicker part of which has an
average thickness between 20 mm and 30 mm and the following
properties at mid-thickness: a tensile yield stress
R.sub.p0.2(L)>340 MPa and optionally tensile
R.sub.p0.2(L)>360 MPa and K.sub.1C L-T>41 MPa m.sup.1/2 and
optionally 44 MPa m.sup.1/2 and the thinnest part of which has an
average thickness between 10 mm and 20 mm and the following
properties at mid-thickness: a tensile yield stress
R.sub.p0.2(L)>440 MPa and optionally tensile
R.sub.p0.2(L)>480 MPa and K.sub.1C L-T>28 MPa m.sup.1/2 and
optionally 32 MPa m.sup.1/2.
9. The rolled product according to claim 8 wherein said
heat-treated aluminum alloy is selected from the group consisting
of AA2050, AA2060, AA2076, AA2196 and AA2296.
10. A lower wing skin obtained from a rolled product according to
claim 8.
11. The rolled product of variable thickness according to claim 7
having a thicker part and a thinner part, the thickness of which
differs by at least 10% and the thicker part of which has an
average thickness between 20 mm and 30 mm and the following
properties at mid-thickness: a tensile yield stress
R.sub.p0.2(L)>580 MPa and optionally tensile
R.sub.p0.2(L)>590 MPa and K.sub.1C L-T>30 MPa m.sup.1/2 and
optionally 32 MPa m.sup.1/2 and the thinnest part of which has an
average thickness between 10 mm and 20 mm and the following
properties at mid-thickness: a tensile yield stress
R.sub.p0.2(L)>600 MPa and optionally tensile
R.sub.p0.2(L)>625 MPa and K.sub.1C L-T>18 MPa m.sup.1/2 and
optionally 20 MPa m.sup.1/2.
12. The rolled product according to claim 11 wherein said
heat-treatable aluminum alloy is selected from the group consisting
of AA2195, AA2295 and AA2055.
13. An upper wing skin obtained from a rolled product according to
claim 11.
14. A rolled product of variable thickness obtained by the process
according to claim 1 capable of being used for manufacture of a
monolithic structural element for aircraft and optionally as an
upper and/or lower wing skin.
15. A rolled product according to claim 14 wherein the volume of
material to be removed by machining between said rolled product and
said structural element is at least 10% lower and optionally at
least 15% lower than the volume of material to be removed between a
metal sheet/plate and the same structural element and/or the convex
envelope of said structural element does not deviate by more than 8
mm and optionally more than 5 mm from said rolled product.
Description
TECHNICAL FIELD OF THE INVENTION
[0001] The invention relates to rolled products and structural
elements made of aluminum alloy, particularly for aircraft
construction.
BACKGROUND OF RELATED ART
[0002] While the competition between the materials for aeronautical
construction intensifies, the commercial criteria in the selection
of solutions are sometimes crucial. The manufacturer is primarily
interested in the price per kilogram of materials in flight which
corresponds to the product of the price per kilogram by the "buy to
fly" ratio. The "buy to fly" ratio is the ratio between the raw
material purchased by the aircraft manufacturer and the raw
material mounted in the flying structure. The integral machining of
aluminum parts from plates sometimes leads to a significant "buy to
fly" ratio, notably for parts such as wing panels for which the
required thickness is higher in the area of the wing root than at
the wing tip. A plate is a rolled product having a rectangular
cross-section of uniform thickness. For the fabrication of
aeronautical structural elements, plates are currently used
regardless of the final geometry of the part produced. Modification
of the geometry of the plate, even if it is justified to save
material has not yet been adopted by aircraft manufacturers as it
presents disadvantages in terms of manufacturing, inspection and
handling and because it does not allow for rapid transfer directly
to the existing methods.
[0003] In addition, it is advantageous to produce monolithic
metallic structural elements having variable properties in space so
to obtain an optimum compromise of properties in each zone.
[0004] FR 2 707 092 describes a method for manufacturing structural
age-hardened products, having continuously variable properties in
at least one direction, in which aging is performed by bringing one
end to temperature T and the other end to a temperature t in a
special furnace comprising a hot chamber and a cold chamber
connected through a heat pump.
[0005] WO 2005/098072 describes a method for manufacturing in which
at least one step of the aging treatment is carried out in a
furnace with a controlled thermal profile comprising at least two
zones or groups of zones Z.sub.1 and Z.sub.2 with initial
temperatures T.sub.1 and T.sub.2 in which the length of the two
zones is at least one meter.
[0006] WO2007/122314 relates to a method for manufacturing a
work-hardened product or a monolithic multi-functional structural
element made of an aluminum alloy comprising a hot working step
characterized in that after the hot working step, it also comprises
at least one working step by cold plastic deformation in which
different general deformations are imposed on at least two zones of
the structural element, with a difference of at least 2% and
preferably at least 3%. However, the methods described in this
application are not implemented on an industrial scale.
[0007] Furthermore, US 2005/0279433 describes a method of
flat-rolling a plate to obtain a variable thickness along its
length, particularly suitable for aluminum or magnesium plates.
[0008] The problem addressed by this invention is to develop a
method for manufacturing rolled products and monolithic structural
elements made of aluminum alloy, notably for aircraft construction,
having an improved "buy to fly" ratio and presenting compromises of
optimized properties in each part.
SUBJECT OF THE INVENTION
[0009] A first subject of the invention is a method for
manufacturing a rolled product of variable thickness made of
heat-treatable aluminum alloy, in which [0010] a. a slab made of
heat-treatable aluminum alloy is cast, [0011] b. optionally, said
slab is homogenized, [0012] c. said optionally homogenized slab is
hot rolled, by achieving a lengthwise thickness variation to obtain
a rolled product of variable thickness, having a thicker part and a
thinner part, the difference in thickness of which is at least 10%,
[0013] d. said rolled product of variable thickness is solution
heat-treated and quenched, [0014] e. said rolled product of
variable thickness, thus solution heat-treated and quenched, is
stress relieved by controlled stretching, with a permanent set of
at least 1% in the thickest part, [0015] f. the rolled product so
obtained is naturally or artificially aged.
[0016] Another subject of the invention is a rolled product of
variable thickness obtained by the method according to the
invention having a thicker part and a thinner part, the thickness
of which differs by at least 10% and having the following
properties at mid-thickness: a tensile yield stress R.sub.p0.2 (L)
in the thinnest part at least 5% greater than that in the thickest
part and a fracture toughness K.sub.1C L-T in the thickest part at
least 15% greater than that in the thinnest part.
[0017] Yet another subject of the invention is the use of a rolled
product of variable thickness obtained by the method according to
the invention as a monolithic structural element for aircraft and
preferably as an upper or lower wing skin.
DESCRIPTION OF THE FIGURES
[0018] FIG. 1: Different geometry examples of rolled product of
variable thickness obtained by the method according to the
invention.
[0019] FIG. 2: Permanent set during stress relieving by controlled
stretching according to the position in the length for the rolled
product of variable thickness of the example.
DESCRIPTION OF THE INVENTION
[0020] Unless otherwise stated, all indications relative to the
chemical composition of the alloys are expressed in percentage by
weight. The names of alloys follow the rules of The Aluminum
Association, known to the skilled person. The metallurgical tempers
and the thermal heat treatments are defined in European standard EN
515. The chemical composition of standardized aluminum alloys is
defined for example in standard EN 573-3. The tensile static
mechanical properties, in other words the ultimate tensile strength
R.sub.m, the conventional tensile yield stress at 0.2% offset
(R.sub.p0.2) and elongation at break A %, are determined by a
tensile test according to standard EN ISO 6892-1, sampling and test
direction being defined by standard EN 485-1. The yield stress
under compression is measured at 0.2% of plastic deformation under
compression as per standard ASTM E9. The plane strain fracture
toughness measurement K.sub.1C is conducted as per ASTM E399. In
the case where K.sub.1C values outside this standard are obtained,
the value of K.sub.1C indicated is K.sub.Q, measured with the
thickest CT specimen that can be taken from the rolled product, and
a length/thickness ratio of the specimen of 2.
[0021] Unless otherwise specified, the definitions of European
standard EN 12258-1 apply: in particular, the term
"non-heat-treatable alloy" is defined as an alloy that cannot be
substantially hardened by heat treatment, and the term
"heat-treatable alloy" is defined for an alloy that can be hardened
by an appropriate heat treatment.
[0022] The term "structural element" refers to an element used in
mechanical engineering for which the static and/or dynamic
mechanical properties are of particular importance for the
performance and the integrity of the structure, and for which a
structural analysis is generally prescribed or carried out. This is
typically a mechanical part whose failure is likely to endanger the
safety of said construction, its users or others. In the context of
the present invention a structural element is typically a part
mounted in a flying structure. For an aircraft, these structural
elements include the parts which make up the fuselage, such as the
fuselage skin, stringers, bulkheads, and circumferential frames,
the wings (such as the upper or lower wing skin), stringers or
stiffeners, ribs and spars and the tail unit, made up of horizontal
and vertical stabilizers, as well as floor beams, seat tracks and
doors.
[0023] Within the scope of the present invention, the term
"monolithic structural element" refers to a structural element that
was obtained from a single piece of rolled semifinished product,
without assembly with another piece through riveting, welding or
bonding.
[0024] According to the invention, a rolled product of variable
thickness made of heat-treatable aluminum alloy is obtained by a
method in which: [0025] a. a slab made of heat-treatable aluminum
alloy is cast, [0026] b. optionally, said slab is homogenized,
[0027] c. said optionally homogenized slab is hot rolled, by
achieving a lengthwise thickness variation to obtain a rolled
product of variable thickness, having a thicker part and a thinner
part, the difference in thickness of which is at least 10%, [0028]
d. said rolled product of variable thickness is solution
heat-treated and quenched, [0029] e. said rolled product of
variable thickness, thus solution heat-treated and quenched, is
stress relieved by controlled stretching, with a permanent set of
at least 1% in the thickest part, [0030] f. the rolled product so
obtained is naturally or artificially aged.
[0031] The method according to the invention is particularly
advantageous for alloys of the 2XXX series for which the stretching
and compression properties after ageing are increased by the
deformation between quenching and ageing. The process is especially
advantageous for alloys of the 2XXX series containing at least 0.5%
by weight of lithium in a T8 or T8X metallurgical temper as the
tensile properties after ageing are particularly increased by the
deformation between quenching and aging for this type of alloy.
[0032] The homogenization of the rolling slab is particularly
advantageous to avoid breakage during rolling, to facilitate
solution heat-treatment and to ensure better control of the
granular structure.
[0033] Hot rolling to a variable thickness is performed to obtain a
lengthwise difference in thickness of at least 10% between the
thickest part and the thinnest part. The variation in thickness is
obtained either progressively over a great length, which may
include the entire length of the rolled product itself, or by at
least one relatively local variation that nevertheless helps to
prevent breakage during stretching as a result of stress
concentration, for example over a length of 0.5 m. The terms
"thickest part" or "thinnest part" designate the continuous
portions of the rolled product, measuring at least one meter in
length, whose average thickness is the highest or the lowest,
respectively. The difference in thickness, expressed as a
percentage, is equal to the difference between the thickness of the
thickest part and that of the thinnest part divided by the
thickness of the thinnest part, the thickness of the thickest part
being the average thickness of the thickest part and the thickness
of the thinnest part being the average thickness of the thinnest
part. Advantageously, said difference in thickness is at least 20%.
In an embodiment of the invention, said difference in thickness is
at least 30%. Typically, the difference in thickness between the
thickest part and the thinnest part is approximately 2 mm or 4 mm
or more depending on the thickness. Preferably, the thickness is
homogenous along the width. The variation in thickness can be
continuous over the entire length of the rolled product, as
illustrated in FIG. 1a or have parts of uniform thickness that are
interconnected by parts of variable thickness having a length of
approximately one meter or more, as illustrated in FIG. 1b. In an
embodiment of the invention illustrated in FIG. 1c, the thickness
of the rolled product of variable thickness is identical at both
ends, the thickest part or the thinnest part typically being
located at mid-length. In this embodiment, the rolled product is
cut into two halfway along its length before machining to obtain a
structural element. This embodiment is advantageous because during
stretching, the thickness of the parts located in the jaws is
identical.
[0034] The thickness of said rolled product is advantageously
between 10 mm and 50 mm and preferably between 12 mm and 30 mm. In
an embodiment of the invention, the thickest part has a thickness
between 20 mm and 30 mm, and the thinnest part has a thickness
between 10 mm and 20 mm.
[0035] Advantageously, the length of said rolled product is between
5 m and 40 m and preferably between 10 m and 30 m.
[0036] The duration and temperature of the rolled product's
solution heat-treatment process is sufficient to ensure that
solution heat-treatment is satisfactory in the thickest part. Thus,
solution heat-treatment is also ensured in the thinnest part.
[0037] Similarly, quenching is dimensioned for the thickest part of
the product.
[0038] After quenching, the internal stresses are relieved by
controlled stretching. Furthermore, the rolled products with
variable thickness obtained must be cut and/or machined to produce
structural elements, notably for aircraft, and during these steps
the internal stresses must be minimal. A permanent set of at least
1% in the thickest part is thus required. In addition, in 2XXX
series alloys, this permanent set is generally a prerequisite for
obtaining the targeted mechanical properties.
[0039] During controlled stretching of the product of variable
thickness, the permanent set varies according to the position along
the length. This variation has been identified as a difficulty
owing to the inspection problem regarding the product obtained.
Surprisingly however, this variation is an advantage in obtaining
products with optimal properties throughout. The permanent set is
lower in the thick part than in the thin part. Typically, the
permanent set in the thinnest part is at least 3% when the
permanent set in the thickest part is at least 1%. For the majority
of 2XXX alloys, a greater permanent set leads to greater mechanical
strength while the fracture toughness is high when the set is less,
notably for T8 tempers. However, beyond a certain threshold, the
gain in mechanical strength obtained through permanent set during
controlled stretching becomes low and the advantage of balancing
properties is thus negligible while the practical problems
associated with achieving a high strain rate are significant.
Advantageously, the permanent set in the thinnest part is thus at
most 8% and preferably it is at most 6%. For aeronautical
structural elements such as lower wing skin or upper wing skin, the
desired properties are high mechanical strength and sufficient
fracture toughness at the wing tip and a high fracture toughness
and sufficient mechanical strength toward the wing root. In
addition, for wing panels, a greater thickness is required at the
wing root than at the wing tip. In this way, the structural element
has a shape closer to the rolled product derived from the process
according to the invention than in prior art in which the
structural element is machined from a metal sheet. Advantageously,
the volume of material, i.e. of aluminum alloy, to be removed by
machining between the rolled product derived from the process
according to the invention and the structural member is at least
10% lower and preferably at least 15% lower than the volume of
material to be removed between a metal sheet/plate and the same
structural element. Preferably, the convex envelope of the
structural element does not deviate by more than 8 mm and
preferably by more than 5 mm from the rolled product derived from
the process according to the invention. The convex envelope of an
object is the smallest convex set among those that contain it, a
convex set being a geometrical object such that each time two
points A and B are taken, the segment [A, B] joining them is
entirely contained therein. The method according to the invention
thus leads to structural elements, notably wing panels, that are
particularly well suited to the needs of aircraft manufacturers:
the thickness is greatest in the area having the highest fracture
toughness which is appropriate for the wing root, and the thickness
lowest in the area having the lowest mechanical strength which will
be appropriate for the wing tip. The "buy to fly" ratio and the
properties of the product are thus improved simultaneously; however
the thickness of the various parts is preferably chosen based on
the final properties sought, taking into account the changes in the
final properties with the permanent set during stretching, and not
as a function of the shape of the structural element.
[0040] Advantageously, the permanent set during controlled
stretching is between 1% and 3% in the thickest part and between 4%
and 6% in the thinnest part.
[0041] After stress relieving by controlled stretching, the rolled
product is naturally aged to obtain a T3 or T3X temper or
artificially aged. Preferably, artificial aging leads to a T8 or
T8X temper.
[0042] Alloys of the 2XXX series AA2022, AA2023, AA2024, AA2024A,
AA2124, AA2224, AA2324, AA2424 AA2524, AA2026 and AA2027 are
particularly suited for implementing the process according to the
invention at a T3 or T3X temper.
[0043] Alloys of the 2XXX series AA2618, AA2219, AA2519, AA2124,
AA2139, AA2050, AA2055, AA2060, AA2076, AA2090, AA2091, AA2094,
AA2095, AA2195, AA2295, AA2196, AA2296, AA2097, AA2197, AA2297,
AA2397, AA2098, AA2198, AA2099 and AA2199 are particularly suited
for implementing the process according to the invention at T8 or
T8X temper.
[0044] The rolled product of variable thickness so obtained is
advantageously used to manufacture monolithic structural elements
for aircraft. The structural element so obtained exhibits
advantageous properties in the thickest part and in the thinnest
part. The use of a rolled product of variable thickness obtainable
by the process according to the invention for the fabrication of an
upper or lower wing skin is particularly advantageous.
[0045] The rolled product of variable thickness obtained by the
process according to the invention exhibits a thicker part and a
thinner part, the thickness of which differs by at least 10% and
having the following properties at mid-thickness: a tensile yield
stress R.sub.p0.2 (L) in the thinnest part at least 5% greater than
that in the thickest part and a fracture toughness K.sub.1C L-T in
the thickest part at least 15% greater than that in the thinnest
part. Advantageously, when the tensile yield stress R.sub.p0.2 (L)
in the thinnest part is at least 5% greater than that in the
thickest part, the fracture toughness K.sub.1C L-T in the thickest
part is at least 40% greater than that in the thinnest part and
when the fracture toughness K.sub.1C L-T in the thickest part is at
least 15% greater than that in the thinnest part, the tensile yield
stress R.sub.p0.2 (L) in the thinnest part is at least 25% greater
than that in the thickest part. A wing skin obtained from a rolled
product according to this embodiment is particularly
advantageous.
[0046] In an embodiment of the invention, the rolled product of
variable thickness is obtained with a 2XXX alloy containing at
least 0.5% of lithium by weight, and advantageously an alloy chosen
from AA2050, AA2060, AA2076, AA2196 and AA2296 and presents for a
T8 or T8X temper a thicker part and a thinner part, the thickness
of which differs by at least 10% and the thicker part of which has
an average thickness between 20 mm and 30 mm and the following
properties at mid-thickness: a tensile yield stress
R.sub.p0.2(L)>340 MPa and preferably tensile
R.sub.p0.2(L)>360 MPa and K.sub.1C L-T>41 MPa m.sup.1/2 and
preferably 44 MPa m.sup.1/2 and the thinnest part of which has an
average thickness between 10 mm and 20 mm and the following
properties at mid-thickness: tensile R.sub.p0.2(L)>440 MPa and
preferably tensile R.sub.p0.2(L)>480 MPa and K.sub.1C L-T>28
MPa m.sup.1/2 and preferably 32 MPa m.sup.1/2. A lower wing skin
obtained from a rolled product according to this embodiment is
particularly advantageous.
[0047] In another embodiment of the invention, the rolled product
of variable thickness is obtained with a 2XXX alloy containing at
least 0.5% of lithium by weight, and advantageously an alloy chosen
from AA2195, AA2295 and AA2055 and presents for a T8 or T8X temper
a thicker part and a thinner part, the thickness of which differs
by at least 10% and the thicker part of which has an average
thickness between 20 mm and 30 mm and the following properties at
mid-thickness: a tensile yield stress R.sub.p0.2(L)>580 MPa and
preferably tensile R.sub.p0.2(L)>590 MPa and K.sub.1C L-T>30
MPa m.sup.1/2 and preferably 32 MPa m.sup.1/2 and the thinnest part
of which has an average thickness between 10 mm and 20 mm and the
following properties at mid-thickness: tensile R.sub.p0.2(L)>600
MPa and preferably tensile R.sub.p0.2(L)>625 MPa and K.sub.1C
L-T>18 MPa m.sup.1/2 and preferably 20 MPa m.sup.1/2. A wing top
skin obtained from a rolled product according to this embodiment is
particularly advantageous.
EXAMPLES
[0048] In this example, for various alloys, a rolled product
measuring 20 m in length is produced, the thickness of which varies
continuously between one end of thickness 15.7 mm and the other end
of thickness 22 mm.
[0049] Three alloys are considered: alloys AA2195, AA2050 and
AA2196. Alloy 2196 has the advantage of having a density of
typically 2.64 as opposed to approximately 2.70 for the other two
alloys. Alloy 2196 may also have a resistance to fatigue crack
propagation greater than that of alloy 2050.
[0050] Plates made of AA2195, AA2050 and AA2196 alloy are cast and
homogenized. The rolling slabs are hot-rolled so as to obtain a
rolled product measuring 20 m in length, the thickness of which
varies continuously between one end of thickness 15.7 mm and the
other end of thickness 22 mm. The rolled products of variable
thickness thus obtained are solution heat-treated and quenched. The
rolled products of variable thickness, thus solution heat-treated
and quenched, are then stress relieved by controlled stretching.
The permanent set obtained is presented based on the position along
the length in FIG. 2, the thickness being 15.7 mm for position "0
m" and 22 mm for position "20 m". The rolled products are then aged
to T8 temper.
[0051] The mechanical properties measured at mid-thickness,
obtained at each end, are presented in Table 1.
TABLE-US-00001 TABLE 1 Mechanical properties obtained at
mid-thickness. 22 mm thick part 15.7 mm thick part Rp.sub.0.2 L
Rp.sub.0.2 L K.sub.1C Rp.sub.0.2 L Rp.sub.0.2 L K.sub.1C Stretching
Compressive (MPa m.sup.1/2) Stretching Compressive (MPa M.sup.1/2)
Alloy (MPa) (MPa) L-T ( (MPa) (MPa) L-T AA2195 590 600 33 635 620
22 AA2050 380 45 505 38 AA2196 350 44 450 30
[0052] For alloy AA2195, the yield stress R.sub.p0.2L is 8% greater
in the thinnest part than in the thickest part and the fracture
toughness K.sub.1CL-T is 50% greater in the thickest part than in
the thinnest part. For alloy AA2050, the yield stress R.sub.p0.2L
is 33% greater in the thinnest part than in the thickest part and
the fracture toughness K.sub.1CL-T is 18% greater in the thickest
part than in the thinnest part. For alloy AA2196, the yield stress
R.sub.p0.2L is 29% greater in the thinnest part than in the
thickest part and the fracture toughness K.sub.1CL-T is 47% greater
in the thickest part than in the thinnest part. Alloy AA2196 also
has the advantage of being less dense than alloy AA2050.
* * * * *